[Federal Register Volume 79, Number 248 (Monday, December 29, 2014)]
[Proposed Rules]
[Pages 77972-77975]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-30270]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-040-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-
300, A340-500, and A340-600 series airplanes. This proposed AD was
prompted by a report of skin disbonding on a composite side panel of a
rudder installed on an A310 airplane. This proposed AD would require a
review of the maintenance records of the rudder to determine if any
composite side shell panel repair has been done; a thermography
inspection limited to the repair areas or complete side shells, as
applicable, to identify possible in-service rudder repairs, damages, or
fluid ingress; and applicable related investigative and corrective
actions. We are proposing this AD to detect and correct the rudder skin
disbonding, which could affect the structural integrity of the rudder,
and could result in reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by February 12,
2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac
[[Page 77973]]
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80;
email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0928; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0928;
Directorate Identifier 2014-NM-040-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2014-0033, dated February 4, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500,
and A340-600 series airplanes. The MCAI states:
A case of skin disbonding was reported on a composite side panel
of a rudder installed on an A310 aeroplane.
The investigation results revealed that this disbonding started
from a skin panel area previously repaired in-service in accordance
with the Structural Repair Manual (SRM).
The initial damage has been identified as a disbonding between
the core and skin of the repaired area. This damage may not be
visually detectable and likely propagates during normal operation
due to the variation of pressure during ground-air-ground cycles.
Composite rudder side shell panels are also installed on A330
and A340 aeroplanes, which may have been repaired in-service using a
similar method.
This condition, if not detected and corrected, could affect the
structural integrity of the rudder, possibly resulting in reduced
control of the aeroplane.
For the reasons described above, this [EASA] AD requires a one-
time thermography inspection of a repaired rudder or a rudder whose
maintenance records are incomplete and, depending on findings,
accomplishment of applicable corrective and follow-up actions
[including repetitive inspections.
The related investigative actions in this AD include, as
applicable, an ultrasonic inspection, an elasticity laminate checker
inspection, a tap test inspection, detailed inspections, thermography
inspections, and ventilation of the core. The repetitive inspections
include detailed inspections and thermography inspections. The
corrective actions in this AD include repairs.
The compliance time for the related investigative actions is before
further flight after accomplishing the applicable inspection required
by paragraph (g)(1) or (g)(2)(ii) of this AD.
The intervals for the repetitive inspections are either 900 flight
hours or 1,000 flight cycles, depending on the applicable conditions
identified in the service information.
The compliance times for the corrective actions range, depending on
the applicable conditions identified in the service information, from
before further flight to within 4,500 flight cycles but not to exceed
24 months after accomplishing the applicable inspection required by
paragraphs (g)(1) or (g)(2)(ii) of this AD.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0928.
Relevant Service Information
Airbus has issued the following service information:
Airbus Service Bulletin A330-55-3043, dated February 7,
2013.
Airbus Service Bulletin A340-55-4039, dated February 7,
2013.
Airbus Service Bulletin A340-55-5007, dated February 7,
2013.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 55 airplanes of U.S.
registry.
We also estimate that it would take about 45 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $0 per
product. Based on these figures, we estimate the cost of this proposed
AD on U.S. operators to be $210,375, or $3,825 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed
[[Page 77974]]
AD is mandatory. Comments concerning the accuracy of this burden and
suggestions for reducing the burden should be directed to the FAA at
800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Amend Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-
040-AD.
(a) Comments Due Date
We must receive comments by February 12, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all airplanes identified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F,
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes,
all manufacturer serial numbers.
(2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes, all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Reason
This AD was prompted by a report of skin disbonding on a
composite side panel of a rudder installed on an A310 airplane. We
are issuing this AD to detect and correct the rudder skin
disbonding, which could affect the structural integrity of the
rudder, and could result in reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Review the Maintenance Records
Within 24 months after the effective date of this AD: Review the
maintenance records of the rudder to determine if any composite side
shell panel repair has been accomplished on the rudder since first
installation on an airplane.
(1) If, based on the maintenance record review, any repair
identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA
(Sheet 02) of the service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD is found: Within 24 months
after the effective date of this AD, do a thermography inspection
for repair, damages, and fluid ingress, limited to the repaired
areas, in accordance with the Accomplishment Instructions of the
applicable service information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD:
(i) Airbus Service Bulletin A330-55-3043, dated February 7, 2013
(for Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes).
(ii) Airbus Service Bulletin A340-55-4039, dated February 7,
2013 (for Model A340-211, -212, -213, -311, -312, and -313
airplanes).
(iii) Airbus Service Bulletin A340-55-5007, dated February 7,
2013 (for Model A340-541 and -642 airplanes).
(2) For a rudder for which maintenance records are unavailable
or incomplete, do the actions specified in paragraph (g)(2)(i) and
(g)(2)(ii) of this AD:
(i) No later than 3 months before accomplishment of the
thermography inspection, as required by paragraph (g)(2)(ii) of this
AD, contact Airbus to request related rudder manufacturing reworked
data by submitting the serial number of the rudder to Airbus.
(ii) Within 24 months after the effective date of this AD: Do a
thermography inspection for any repair on complete side shells to
identify and mark any repair, in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD.
(h) Related Investigative Actions, Corrective Actions, and Repetitive
Inspections
After the inspection as required by paragraph (g)(1) or (g)(2)
of this AD: At the applicable compliance times specified in
paragraph 1.E., ``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5
of the applicable service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD, accomplish all applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD;
except as provided by paragraphs (i)(1) and (i)(2) of this AD.
Options provided in the service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD for accomplishing the
actions are acceptable for the corresponding requirements of this
paragraph provided that the related investigative and corrective
actions are done at the applicable times specified in paragraph
1.E., ``Compliance,'' of the applicable service information
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD,
including applicable repetitive inspection intervals. Thereafter
repeat the inspections of the restored and repaired areas at the
applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5 of the applicable
service information specified in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD.
(i) Exceptions to the Service Information
(1) Where the applicable service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD specifies a
compliance time relative to the date of the service information,
this AD requires compliance within the specified compliance time
after the effective date of this AD.
(2) If the service information in paragraphs (g)(1)(i) through
(g)(1)(iii) of this AD specifies to contact Airbus: At the
applicable
[[Page 77975]]
compliance times specified in paragraph 1.E., ``Compliance,'' of the
applicable service information specified in paragraphs (g)(1)(i)
through (g)(1)(iii) of this AD, repair using a method approved by
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA).
(j) Provisions for Certain Airplanes
Airplanes fitted with a rudder having a serial number (S/N) that
is not in the range of S/N TS-1001 through S/N TS-1043 inclusive, S/
N TS-2001 through S/N TS-2074 inclusive, S/N TS-3000 through S/N TS-
3525 inclusive, S/N TS-4001 through S/N TS-4170 inclusive, S/N TS-
6001 through S/N TS-6246 inclusive, or S/N TS-5001 through S/N TS-
5138 inclusive, are not affected by the requirements of paragraphs
(g) and (h) of this AD provided that it is determined that no repair
has been accomplished on the composite side shell panel of that
rudder since first installation on the airplane.
(k) Parts Installation Limitations
As of the effective date of this AD, no person may install, on
any airplane, a rudder, unless the record review and thermography
inspection specified in paragraph (g) of this AD has been done on
that rudder and thereafter all applicable related investigative
actions, repetitive inspections, and corrective actions are done as
required by paragraph (h) of this AD, except as provided in
paragraph (j) of this AD.
(l) Repair Prohibition
As of the effective date of this AD, no person may accomplish a
side shell repair on any rudder using a structure repair manual
procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure
A-GBCAA (Sheet 02) of the service information specified in
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable,
on any airplane.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0033, dated February 4,
2014, for related information. This MCAI may be found in the AD
docket on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0928.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email [email protected];
Internet http://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on December 17, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-30270 Filed 12-24-14; 8:45 am]
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